Method of first-approximation calculation of take-off weight of a light aircraft with a hybrid propulsion system


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Abstract

The article discusses a method for calculating, as a first approximation, the take-off weight of a light aircraft with a hybrid power plant based on piston and electric engines. A brief overview of organizations dealing with hybrid power plants is given.  The influence of the degree of hybridization of the power plant on the take-off weight of the aircraft is shown. The degree of hybridization of a power plant is understood as a relative value characterizing the distribution of the total power of all engines installed on the aircraft between piston and electric engines. The main parameters necessary to determine the take-off weight of an aircraft to a first approximation are presented. The take-off weight of the aircraft is determined to a first approximation from the equation of its existence. Statistical data of aircraft with different types of power plants are provided on the basis of which calculations are carried out. As a first approximation, the relative mass of the hybrid power plant is determined by analyzing the statistical data of light aircraft with piston and electric engines, from which the corresponding graphs are constructed. After the calculations, conclusions were drawn about the optimal range of characteristics of a light aircraft with a hybrid power plant.

About the authors

A. V. Sychev

Moscow Aviation Institute (National Research University)

Author for correspondence.
Email: saavia@mail.ru

Leading Engineer of MAI Advanced Engineering School

Russian Federation

I. V. Arbuzov

Moscow Aviation Institute (National Research University)

Email: i_arbusov@mail.ru

Candidate of Science (Engineering), Senior Researcher, Associate Professor

Russian Federation

Yu. A. Ravikovich

Moscow Aviation Institute (National Research University)

Email: yurav@mai.ru

Doctor of Science (Engineering), Professor, Vice-Rector for Research

Russian Federation

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